CN114486155A - High-enthalpy shock tunnel parameter diagnosis method and system - Google Patents
High-enthalpy shock tunnel parameter diagnosis method and system Download PDFInfo
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- CN114486155A CN114486155A CN202111619055.7A CN202111619055A CN114486155A CN 114486155 A CN114486155 A CN 114486155A CN 202111619055 A CN202111619055 A CN 202111619055A CN 114486155 A CN114486155 A CN 114486155A
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Abstract
The invention discloses a method and a system for diagnosing flow field parameters of a high-enthalpy shock tunnel, and relates to the field of high-enthalpy shock tunnel tests. The method of the invention utilizes the high enthalpy shock tunnel, adopts the contact measurement technology and the non-contact spectrum measurement technology, measures the parameters of the resident chamber at the tail end of the shock tube and the parameters of the free flow of the spray pipe, and diagnoses the flow field of the high enthalpy shock tunnel. The invention utilizes the contact measurement technology, the laser schlieren technology, the non-contact absorption spectrum measurement technology, the non-contact emission spectrum measurement technology and the multi-component multi-temperature numerical simulation technology to diagnose the parameters of the high-enthalpy shock tunnel shock tube terminal chamber and the parameters of the free flow of the jet tube, thereby not only obtaining the temperature, the pressure and the component category and the component concentration of the flow field, but also obtaining the non-equilibrium state information of the flow field and the effective operation time of the wind tunnel.
Description
Technical Field
The invention relates to a method and a system for diagnosing parameters of a high-enthalpy shock tunnel, belonging to the field of hypersonic aerodynamic tests.
Background
With the continuous progress of human aerospace science and technology, various supersonic and hypersonic reentrant flying objects may exist in the near-earth space, when the reentrant body returns to the atmosphere at a high speed, strong friction exists between the reentrant body and the atmosphere, a strong shock wave for body detachment is formed at the front end of the reentrant body, under the action of the strong compression of the shock wave, a large amount of kinetic energy of the aircraft is converted into heat energy, high enthalpy flow is formed, and complex physicochemical changes such as excitation, dissociation, recombination and ionization of gas molecular vibration energy are caused.
To study such reentry phenomena, reentry physics ground simulations are typically performed using high enthalpy shock tunnels. Then enters into the physical ground to simulate the high enthalpy flow, which is characterized by strong spontaneous emission characteristic, air dissociation or even ionization, and abundant information content, and is a precious test data for researching the balance and non-balance properties of the flow.
Energy level transition generated in complex physicochemical change processes such as excitation, dissociation, recombination and ionization of gas molecules in high-enthalpy flow can cause energy change, and the change can cause the molecules to have specific spectral lines. The present invention was developed based on the above background.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the characteristics of high temperature and high pressure test gas generation of the high enthalpy shock tunnel and short effective flow field time, the method and the system for diagnosing the high enthalpy flowing gas information are provided by utilizing a contact measurement technology, a laser schlieren technology, a non-contact absorption spectrum technology, a non-contact emission spectrum technology and a multi-component multi-challenge numerical simulation technology. The precision of the high enthalpy shock tunnel test flow field is improved, and more accurate free flow parameters can be obtained.
The technical scheme of the invention is as follows: a high enthalpy shock tunnel flow field parameter diagnosis system comprises: the device comprises a piezoelectric sensor, a total pressure sensor, an absorption spectrum system, an emission spectrum system, a pitot pressure probe, a static pressure probe, a stationary point heat flow probe, a first data processing system and a second data processing system;
mounting a plurality of piezoelectric sensors on a shock tube, and mounting a total pressure sensor at the tail end of the shock tube; installing a non-contact absorption spectrum system and a collimator and a detector of an emission spectrum system near a total pressure sensor at the tail end of the shock tube, and installing the non-contact absorption spectrum system and the collimator and the detector of the emission spectrum system in a test section; installing a pitot pressure probe, a static pressure probe and a stationing point heat flow probe on a bent frame in the test section, and measuring the pitot pressure, the static pressure and the stationing point heat flow of a flow field of the test section; the data measured by the non-contact absorption spectrum system, the emission spectrum system, the picot pressure probe, the static pressure probe and the stagnation point heat flow probe are respectively sent to the first data processing system and the second data processing system through optical fibers or data lines for data processing.
The measurement wave band of the emission spectrum system is 0.1-6 μm, and is determined according to the spectrum information of the free flow parameters of the shock tube terminal resident chamber and the high enthalpy jet tube.
The non-contact absorption spectrum system adopts NO and O lasers to measure the concentration of free flow components NO and O of a shock tube terminal resident chamber and a spray tube; measuring the temperature of the free flow of the shock tube tail end resident chamber and the high enthalpy spray tube by using a near infrared detection device and a spectral line; and a near-infrared detection device is arranged on the cross bent of the test section, two spectral lines are adopted for measuring the speed, and the included angle of two optical paths for measuring the speed is 30-60 degrees.
The laser schlieren system penetrates through a self-luminous flow field at the outlet of the high-enthalpy spray pipe, self-luminescence is filtered, and clear ball head de-body shock wave distance is shot; the monochromatic laser light source penetrates through the strong light and high temperature area, and a clear flow field structure can be observed by installing a matched optical filter in front of the camera.
The first data acquisition system and the second data acquisition system adopt a PXI test platform, multi-channel cascade is realized by adopting a cascade mode of a plurality of sets of PXIe chassis, and the acquisition frequency is more than 100 kHz.
A high enthalpy shock tunnel flow field parameter diagnosis method comprises the following steps:
installing a plurality of piezoelectric sensors on a shock tube, and installing a total pressure sensor at the tail end of the shock tube; installing a non-contact absorption spectrum system and a collimator and a detector of an emission spectrum system near a total pressure sensor at the tail end of the shock tube, and installing the non-contact absorption spectrum system and the collimator and the detector of the emission spectrum system in a test section; a pitot pressure probe, a static pressure probe and a standing point heat flow probe are arranged on a bent frame in the test section and are used for measuring pitot pressure, static pressure and standing point heat flow of a flow field of the test section; respectively sending data measured by the non-contact absorption spectrum system, the emission spectrum system, the skin pressure probe, the static pressure probe and the stagnation point heat flow probe to a first data processing system and a second data processing system through optical fibers or data lines for data processing;
measuring a time interval delta t of the incident shock wave passing through the piezoelectric sensor by using the piezoelectric sensor on the upper wall surface of the shock tube, and calculating the velocity V of the incident shock wave to be delta L/delta t according to the distance delta L between the piezoelectric sensors;
step three, mounting a total pressure sensor by utilizing the wall surface of the tail end of the shock tube, and measuring the total pressure P of the shock tube tail end resident chamber after the incident shock wave is reflected0；
Step four, measuring the translation temperature and the NO/O component concentration of the shock tube tail end resident chamber gas and the free flow gas of the high enthalpy spray pipe (3) by using a non-contact absorption spectrum system;
measuring vibration temperature and component spectrum information of the shock tube tail end resident chamber gas and the spray tube free flow gas by using an emission spectrum system;
installing a ball head on a cross bent of the test section, and measuring the structure of a flow field around the ball head by using a laser schlieren system to obtain the distance of the shock wave of the head of the ball head;
step seven, mounting a skin pressure probe, a static pressure probe and a standing point heat flow probe on a cross-shaped bent frame of the test section to obtain skin pressure, static pressure and standing point heat flow of a flow field;
step (eight), measuring and obtaining the incident shock wave velocity V and the total pressure P of the shock wave tube tail end resident chamber by using the step (two) and the step (three)0Calculating the shock tube tail end resident chamber parameter under the high-temperature state condition (2000K-10000K) by adopting a thermodynamic numerical model of high-temperature air and a quasi-one-dimensional shock tube theory, comparing the shock tube tail end resident chamber parameter with the temperature of the shock tube tail end resident chamber measured in the step (IV) and the concentration of NO/O components, if the deviation of the data of the shock tube tail end resident chamber parameter and the temperature of the shock tube tail end resident chamber measured in the step (IV) is greater than a set threshold value a, modifying the thermodynamic numerical model, and iterating again until the deviation of the data of the shock tube tail end resident chamber parameter and the data of the shock tube tail end resident chamber measured in the step (IV) is less than or equal to the set threshold value a;
step (nine), taking the shock tube end resident chamber parameter iteratively completed in the step (eight) as an input numerical value, calculating the initial condition of the high-enthalpy spray tube flow field, calculating the high-enthalpy spray tube flow field by using a multi-component multi-temperature thermochemistry unbalanced numerical simulation method, and calculating the obtained high-enthalpy spray tube outlet parameter; and (4) comparing the outlet parameters of the high enthalpy spray pipe with the measured data in the steps (three) to (seven), if the deviation of the data of the high enthalpy spray pipe and the measured data of the high enthalpy spray pipe is greater than a set threshold value b, modifying the numerical model, and iterating again until the deviation of the data of the high enthalpy spray pipe and the measured data of the high enthalpy spray pipe is less than or equal to the set threshold value b.
The method for diagnosing the flow field parameters of the high-enthalpy shock wave wind tunnel measures the gas components of the high-enthalpy jet pipe resident chamber and the free flow at the outlet of the jet pipe by using the emission spectrum system, and judges the effective running time t1 of the wind tunnel according to whether the driving gas components exist or not;
measuring the NO/O concentration of free flow at the resident chamber of the high enthalpy spray pipe and the outlet of the spray pipe by using a non-contact absorption spectrum system, and judging the effective running time t2 of the wind tunnel;
judging the effective wind tunnel operation time t3 according to the shock wave distance of the spherical head off-body shot by the laser schlieren system and the shock wave distance of the off-body; and taking the minimum value of the time t1, the time t2 and the time t3 as the effective running time of the wind tunnel.
The wavelength range of a monochromatic laser light source adopted in the laser schlieren system is 520-720 nm.
Compared with the prior art, the invention has the beneficial effects that:
the invention utilizes the contact measurement technology, the laser schlieren technology, the non-contact absorption spectrum measurement technology, the non-contact emission spectrum measurement technology, the multicomponent multi-temperature numerical simulation technology and the like to jointly diagnose the parameters of the high enthalpy shock tunnel shock tube tail end chamber and the parameters of the free flow of the jet tube, thereby not only obtaining the temperature, the pressure, the component category and the component concentration of the flow field, but also obtaining the information of the nonequilibrium state of the flow field and the effective operation time of the wind tunnel. The method for diagnosing the flow field parameters of the high-enthalpy shock tunnel can be used for building a high-enthalpy flow field parameter measuring platform, has very high sensitivity, continuous time resolution and quick time response, and is a better optimal method.
Drawings
Fig. 1 is a flow chart of a high enthalpy shock tunnel flow field parameter diagnosis method related to the present invention.
Fig. 2 is a schematic view of a high enthalpy shock tunnel flow field parameter diagnosis method according to the present invention.
The system comprises a shock tube 1, a diaphragm 2, a high enthalpy spray tube 3, a test section 4, a cross bent frame for mounting a sensor 5, an optical window 6, an absorption spectrum system 7, a data processing system 8, an emission spectrum system 9 and a data processing system 10.
Detailed Description
The features and advantages of the present invention will become more apparent and appreciated from the following detailed description of the invention.
The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration. Any embodiment described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other embodiments. While the various aspects of the embodiments are presented in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.
As shown in fig. 2, a high enthalpy shock tunnel flow field parameter diagnosis system includes: a piezoelectric sensor, a total pressure sensor, an absorption spectroscopy system 7, an emission spectroscopy system 9, a pitot pressure probe, a static pressure probe, a stagnation point heat flow probe, a first data processing system 8 and a second data processing system 10;
a plurality of piezoelectric sensors are arranged on the shock tube 1, and a total pressure sensor is arranged at the tail end of the shock tube 1; a non-contact absorption spectrum system 7 and a collimator and a detector of an emission spectrum system 9 are arranged near a total pressure sensor at the tail end of the shock tube 1, and the non-contact absorption spectrum system 7 (an optical fiber probe of the absorption spectrum system 7 is arranged at an optical window 6 of the test section 4) and the collimator and the detector of the emission spectrum system 9 are arranged on the test section 4; a pitot pressure probe, a static pressure probe and a standing point heat flow probe are arranged on a bent frame 5 in the test section 4 and are used for measuring pitot pressure, static pressure and standing point heat flow of a flow field of the test section; the data measured by the non-contact absorption spectroscopy system 7, the emission spectroscopy system 9 and the pitot pressure probe, the static pressure probe and the stagnation point heat flow probe are respectively sent to the first data processing system 8 and the second data processing system 10 for data processing through optical fibers or data lines.
The measurement wave band of the emission spectrum system 9 is 0.1-6 μm, and is determined according to the spectral information of the free flow parameters of the shock tube 1 end dwelling chamber and the high enthalpy jet tube 3.
The non-contact absorption spectrum system 7 adopts NO and O lasers to measure the concentration of the components NO and O of the free flow of the standing chamber and the spray pipe at the tail end of the shock tube 1; measuring the temperature of the free flow of the standing chamber at the tail end of the shock tube 1 and the high-enthalpy spray tube 3 by using a near-infrared detection device and a spectral line; a near-infrared detection device is arranged on a cross bent 5 of the test section, two spectral lines are used for measuring the speed, and the included angle of two optical paths for measuring the speed is 30-60 degrees.
The laser schlieren system penetrates through a self-luminous flow field at the outlet of the high-enthalpy spray pipe 3, self-luminescence is filtered, and clear ball head de-body shock wave distance is shot; the monochromatic laser light source penetrates through the strong light and high temperature area, and a clear flow field structure can be observed by installing a matched optical filter in front of the camera.
The first data acquisition system 8 and the second data acquisition system 10 adopt a PXI test platform, and realize multi-channel cascade by adopting a cascade mode of a plurality of sets of PXIe chassis, and the acquisition frequency is more than 100 kHz.
Referring to fig. 1, the invention provides a method for diagnosing flow field parameters of a high enthalpy shock tunnel, which provides a feasible idea verified by tests for diagnosing the flow field parameters of the high enthalpy shock tunnel, and the method has the key point that a room standing parameter at the tail end of a high enthalpy shock tunnel shock tube 1 and a free flow parameter of a spray tube are jointly diagnosed by utilizing a contact measurement technology, a laser schlieren technology, a non-contact absorption spectrum measurement technology, a non-contact emission spectrum measurement technology, a multi-component multi-temperature numerical simulation technology and the like, and when a verification result meets the flow field requirements, namely a test measurement result is matched with a numerical simulation result, the diagnosis of the flow field parameters of the high enthalpy shock tunnel is completed. The invention can not only obtain the temperature, pressure, component category and component concentration of the flow field, but also obtain the nonequilibrium information of the flow field and the effective operation time of the wind tunnel.
Step one, a series of piezoelectric sensors are installed on a shock tube 1, and a total pressure sensor is installed at the tail end of the shock tube 1. A non-contact absorption spectrum system 7 and a collimator and a detector of an emission spectrum system 9 are arranged near a total pressure sensor at the tail end of the shock tube 1, and the non-contact absorption spectrum system 7 and the collimator and the detector of the emission spectrum system 9 are also arranged on the test section 4. A pitot pressure probe, a static pressure probe and a stagnation point heat flow probe are arranged on a cross bent 5 in the test section 4, and data measured by a non-contact absorption spectrum system 7, an emission spectrum system 9, the pitot pressure probe, the static pressure probe and the stagnation point heat flow probe are respectively sent to a first data processing system 8 and a second data processing system 10 through optical fibers or data wires for data processing; and a diaphragm 2 is arranged between the shock tube 1 and the high enthalpy jet tube 3.
And step two, measuring the time interval delta t of the incident shock wave passing through the piezoelectric sensors by using the piezoelectric sensors on the upper wall surface of the shock tube 1, and calculating the incident shock wave speed V as delta L/delta t according to the distance delta L between the piezoelectric sensors.
Thirdly, mounting a total pressure sensor on the wall surface of the tail end of the shock tube 1, and measuring the total pressure P of the shock tube 1 tail end resident chamber after the incident shock wave is reflected0Measuring to obtain the incident shock wave velocity V and the total pressure P of the shock wave tube 1 terminal resident chamber0And calculating the room holding parameters under the condition of a high-temperature state by adopting thermodynamic data of high-temperature air.
And step four, measuring the translation temperature, NO/O component concentration and the like of the resident gas at the tail end of the shock tube 1 and the free flow gas of the high enthalpy spray tube 3 by using a non-contact absorption spectrum system 7.
And fifthly, installing an emission spectrum system 9 at the position, close to the total pressure sensor, of the tail end of the shock tube 1 and at the test section, and measuring vibration temperature and component spectrum information of the standing gas at the tail end of the shock tube 1 and the free flow gas of the spray tube 3.
And step six, mounting a ball head in the flow field uniform area of the test section 4, and measuring the structure of the flow field around the ball head by using a laser schlieren system to obtain the distance of the shock wave of the head of the ball head.
And seventhly, mounting a skin pressure probe, a static pressure probe and a stagnation point heat flow probe in the uniform area of the flow field of the test section 4 to obtain skin pressure, static pressure and stagnation point heat flow of the flow field.
Step eight, obtaining the incident shock wave velocity V and the total pressure P of the terminal resident chamber of the shock tube 1 by utilizing the measurement of the step two and the step three0Calculating the terminal chamber standing parameter of the shock tube 1 under a high-temperature state condition (2000K-10000K) by adopting a thermodynamic numerical model of high-temperature air and a quasi-one-dimensional shock tube theory, comparing the terminal chamber standing parameter of the shock tube 1 with the measured temperature of the terminal chamber standing of the shock tube 1 and the concentration of NO/O components, if the deviation of the data of the two is more than 4%, modifying the thermodynamic numerical model, and iterating again until the deviation of the data of the two is less than or equal to 4%;
step nine, taking the parameters of the end resident chamber of the shock tube 1 after iteration in the step eight as input numerical values, calculating initial conditions of a flow field of the high-enthalpy spray tube 3, calculating the flow field of the high-enthalpy spray tube 3 by using a multi-component multi-temperature thermochemical unbalanced numerical simulation method, and calculating outlet parameters of the high-enthalpy spray tube 3; and (3) comparing the outlet parameters of the high enthalpy spray pipe 3 with the measured data in the third step to the seventh step, if the deviation of the data of the high enthalpy spray pipe 3 and the measured data of the third step is more than 6%, modifying the numerical model, and iterating again until the deviation of the data of the high enthalpy spray pipe 3 and the measured data of the seventh step is less than or equal to 6%.
Measuring free flow gas components of a resident chamber of the high enthalpy spray pipe 3 and an outlet of the spray pipe by using an emission spectrum system 9, and judging the effective operation time t1 of the wind tunnel according to whether a driving gas component exists or not;
measuring the NO/O concentration of free flow at the resident chamber and the outlet of the high enthalpy spray pipe 3 by using a non-contact absorption spectrum system 7, and judging the effective running time t2 of the wind tunnel;
judging the effective wind tunnel operation time t3 according to the shock wave distance of the spherical head off-body shot by the laser schlieren system and the shock wave distance of the off-body; and taking the minimum value of the time t1, the time t2 and the time t3 as the effective running time of the wind tunnel.
The invention utilizes the contact measurement technology, the laser schlieren technology, the non-contact absorption spectrum measurement technology, the non-contact emission spectrum measurement technology, the multicomponent multi-temperature numerical simulation technology and the like to jointly diagnose the parameters of the chamber at the tail end of the high enthalpy shock tunnel shock tube 1 and the parameters of the free flow of the jet tube, thereby not only obtaining the temperature, the pressure and the component category and the component concentration of the flow field, but also obtaining the information of the nonequilibrium state of the flow field and the effective operation time of the wind tunnel. The method for diagnosing the flow field parameters of the high-enthalpy shock tunnel can be used for building a high-enthalpy flow field parameter measuring platform, has very high sensitivity, continuous time resolution and quick time response, and is a better optimal method.
Those skilled in the art will appreciate that the invention may be practiced without these specific details.
Claims (13)
1. A high enthalpy shock tunnel flow field parameter diagnosis method is characterized by comprising the following steps:
installing a plurality of piezoelectric sensors on a shock tube (1), and installing a total pressure sensor at the tail end of the shock tube (1); a non-contact absorption spectrum system (7) and a collimator and a detector of an emission spectrum system (9) are arranged near a total pressure sensor at the tail end of the shock tube (1), and the non-contact absorption spectrum system (7) and the collimator and the detector of the emission spectrum system (9) are arranged in the test section (4); a Pitot pressure probe, a static pressure probe and a standing point heat flow probe are arranged on a bent frame (5) in the test section (4) and are used for measuring Pitot pressure, static pressure and standing point heat flow of a flow field of the test section; data measured by the non-contact absorption spectrum system (7), the emission spectrum system (9), the pitot pressure probe, the static pressure probe and the stagnation point heat flow probe are respectively sent to a first data processing system (8) and a second data processing system (10) through optical fibers or data lines for data processing;
measuring a time interval delta t of an incident shock wave passing through a piezoelectric sensor by using the piezoelectric sensor on the upper wall surface of the shock tube (1), and calculating the speed V of the incident shock wave to be delta L/delta t according to the distance delta L between the piezoelectric sensors;
step three, mounting a total pressure sensor by utilizing the wall surface at the tail end of the shock tube (1), and measuring the total pressure P of a room where the tail end of the shock tube (1) resides after the incident shock wave is reflected0；
Step four, measuring the translation temperature and the NO/O component concentration of the resident chamber gas at the tail end of the shock tube (1) and the free flow gas of the high enthalpy spray tube (3) by using a non-contact absorption spectrum system (7);
measuring vibration temperature and component spectrum information of the gas in the room at the tail end of the shock tube (1) and the free flow gas of the spray tube (3) by using the emission spectrum system (9);
step six, mounting a ball head on the cross bent (5) of the test section, and measuring the structure of a flow field around the ball head by using a laser schlieren system to obtain the distance of the shock wave of the head of the ball head;
step seven, mounting a skin pressure probe, a static pressure probe and a stagnation point heat flow probe on the cross bent frame (5) of the test section to obtain skin pressure, static pressure and stagnation point heat flow of a flow field;
step (eight), measuring and obtaining the incident shock wave velocity V and the total pressure P of the terminal resident chamber of the shock tube (1) by using the step (two) and the step (three)0The thermodynamics numerical model of high-temperature air and the quasi-one-dimensional shock tube theory are adopted to calculate the terminal resident chamber parameter of the shock tube (1) under the condition of high temperature,comparing the parameters of the shock tube (1) terminal chamber with the temperature of the shock tube (1) terminal chamber measured in the step (IV) and the concentration of the NO/O component, if the deviation of the data of the two is greater than a set threshold value a, modifying the thermodynamic numerical model, and iterating again until the deviation of the data of the two is less than or equal to the set threshold value a;
step (nine), taking the terminal resident chamber parameter of the shock tube (1) iteratively completed in the step (eight) as an input numerical value, calculating the initial condition of the flow field of the high enthalpy spray tube (3), calculating the flow field of the high enthalpy spray tube (3) by using a multi-component multi-temperature thermochemistry non-equilibrium numerical simulation method, and calculating the outlet parameter of the high enthalpy spray tube (3); and (4) comparing the outlet parameters of the high enthalpy spray pipe (3) with the measured data in the steps (three) to (seven), if the deviation of the data of the high enthalpy spray pipe and the measured data of the high enthalpy spray pipe is greater than a set threshold value b, modifying the numerical model, and iterating again until the deviation of the data of the high enthalpy spray pipe and the measured data of the high enthalpy spray pipe is less than or equal to the set threshold value b.
2. The method for diagnosing the flow field parameters of the high enthalpy shock tunnel according to claim 1, characterized in that: the measurement wave band of the emission spectrum system (9) is 0.1-6 μm, and is determined according to the spectrum information of the free flow parameters of the standing chamber at the tail end of the shock tube (1) and the high enthalpy jet tube (3).
3. The method for diagnosing the flow field parameters of the high enthalpy shock tunnel according to claim 2, characterized in that: the non-contact absorption spectrum system (7) adopts NO and O lasers to measure the concentrations of the components NO and O of the free flow of the terminal resident chamber and the nozzle of the shock tube (1); measuring the temperature of the free flow of a standing chamber at the tail end of the shock tube (1) and the high-enthalpy spray tube (3) by using a near-infrared detection device and a spectral line; a near-infrared detection device is arranged on a cross bent (5) of the test section, two spectral lines are used for measuring the speed, and the included angle of two optical paths for measuring the speed is 30-60 degrees.
4. The method for diagnosing the flow field parameters of the high enthalpy shock tunnel according to claim 3, characterized in that: the laser schlieren system penetrates through a self-luminous flow field at the outlet of the high-enthalpy spray pipe (3), self-luminescence is filtered, and clear shock wave distance of the head part of the ball head is shot; the monochromatic laser light source penetrates through the strong light and high temperature area, and a clear flow field structure can be observed by installing a matched optical filter in front of the camera.
5. The method for diagnosing the flow field parameters of the high enthalpy shock tunnel according to claim 4, characterized in that: the wavelength range of a monochromatic laser light source adopted in the laser schlieren system is 520-720 nm.
6. The method for diagnosing the flow field parameters of the high enthalpy shock tunnel according to claim 5, characterized in that: the first data acquisition system (8) and the second data acquisition system (10) adopt a PXI test platform, and realize multi-channel cascade by adopting a plurality of sets of PXIe chassis cascade modes, wherein the acquisition frequency is more than 100 kHz.
7. The method for diagnosing the flow field parameters of the high enthalpy shock tunnel according to claim 1, characterized in that: measuring free flow gas components of a high enthalpy spray pipe (3) parking chamber and a spray pipe outlet by using an emission spectrum system (9), and judging the effective operation time t1 of the wind tunnel according to whether a driving gas component exists or not;
measuring the NO/O concentration of free flow of a high enthalpy spray pipe (3) parking chamber and a spray pipe outlet by using a non-contact absorption spectrum system (7), and judging the effective operation time t2 of the wind tunnel;
judging the effective wind tunnel operation time t3 according to the shock wave distance of the spherical head off-body shot by the laser schlieren system and the shock wave distance of the off-body; and taking the minimum value of the time t1, the time t2 and the time t3 as the effective running time of the wind tunnel.
8. A high enthalpy shock tunnel flow field parameter diagnosis system is characterized by comprising: a piezoelectric sensor, a total pressure sensor, an absorption spectroscopy system (7), an emission spectroscopy system (9), a pitot pressure probe, a static pressure probe, a stagnation point heat flow probe, a first data processing system (8) and a second data processing system (10);
a plurality of piezoelectric sensors are arranged on the shock tube (1), and a total pressure sensor is arranged at the tail end of the shock tube (1); a non-contact absorption spectrum system (7) and a collimator and a detector of an emission spectrum system (9) are arranged near a total pressure sensor at the tail end of the shock tube (1), and the non-contact absorption spectrum system (7) and the collimator and the detector of the emission spectrum system (9) are arranged in the test section (4); a Pitot pressure probe, a static pressure probe and a standing point heat flow probe are arranged on a bent frame (5) in the test section (4) and are used for measuring Pitot pressure, static pressure and standing point heat flow of a flow field of the test section; the data measured by the non-contact absorption spectrum system (7), the emission spectrum system (9), the pitot pressure probe, the static pressure probe and the stagnation point heat flow probe are respectively sent to a first data processing system (8) and a second data processing system (10) through optical fibers or data lines for data processing.
9. The high enthalpy shock tunnel flow field parameter diagnosis system according to claim 8, characterized in that: the measurement wave band of the emission spectrum system (9) is 0.1-6 μm, and is determined according to the spectrum information of the free flow parameters of the standing chamber at the tail end of the shock tube (1) and the high enthalpy jet tube (3).
10. The high enthalpy shock tunnel flow field parameter diagnosis system according to claim 9, characterized in that: the non-contact absorption spectrum system (7) adopts NO and O lasers to measure the concentrations of the components NO and O of the free flow of the terminal resident chamber and the nozzle of the shock tube (1); measuring the temperature of the free flow of a standing chamber at the tail end of the shock tube (1) and the high-enthalpy spray tube (3) by using a near-infrared detection device and a spectral line; a near-infrared detection device is arranged on a cross bent (5) of the test section, two spectral lines are used for measuring the speed, and the included angle of two optical paths for measuring the speed is 30-60 degrees.
11. The high enthalpy shock tunnel flow field parameter diagnosis system according to claim 10, characterized in that: the laser schlieren system penetrates through a self-luminous flow field at the outlet of the high enthalpy spray pipe (3), self-luminescence is filtered, and clear shock wave distance of the head of the bulb in the head part is shot; the monochromatic laser light source penetrates through the strong light and high temperature area, and a clear flow field structure can be observed by installing a matched optical filter in front of the camera.
12. The high enthalpy shock tunnel flow field parameter diagnosis system according to claim 11, characterized in that: the wavelength range of a monochromatic laser light source adopted in the laser schlieren system is 520-720 nm.
13. The high enthalpy shock tunnel flow field parameter diagnosis system according to claim 12, characterized in that: the first data acquisition system (8) and the second data acquisition system (10) adopt a PXI test platform, and realize multi-channel cascade by adopting a plurality of sets of PXIe chassis cascade modes, wherein the acquisition frequency is more than 100 kHz.
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